U.S. patent number 3,857,042 [Application Number 05/409,996] was granted by the patent office on 1974-12-24 for laser seeker test set.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Ralph E. Brewer, Edward J. Davis, Curtis A. Hamilton, Don E. LaGrange, Eugene R. Sheer.
United States Patent |
3,857,042 |
LaGrange , et al. |
December 24, 1974 |
LASER SEEKER TEST SET
Abstract
A target simlator comprising a sequencing infrared source and a
plurality binary coded inputs is used to test the reaction of a
missile seeker which operates on the principal of a parabolic
mirror being flooded with parallel light rays which in turn are
reflected onto the detector. The light rays are either parallel to
the center line axis of the missile or at some angle thereto. The
angle of these rays with respect to the missile centerline is
detected by the missile guidance system to cause the missile to
track the rays. The target simulator according to the present
invention utilizes this principle without flooding the entire
mirror using a 1/4 inch column of parallel light rays from
sequenced infrared sources.
Inventors: |
LaGrange; Don E. (Los Angeles,
CA), Davis; Edward J. (China Lake, CA), Sheer; Eugene
R. (Ridgecrest, CA), Brewer; Ralph E. (Ridgecrest,
CA), Hamilton; Curtis A. (Ridgecrest, CA) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
|
Family
ID: |
23622799 |
Appl.
No.: |
05/409,996 |
Filed: |
October 26, 1973 |
Current U.S.
Class: |
250/495.1;
244/3.16; 73/1.78 |
Current CPC
Class: |
F41G
7/005 (20130101); F41G 7/004 (20130101) |
Current International
Class: |
F41G
7/00 (20060101); G21h 005/00 () |
Field of
Search: |
;250/495,504,338,340,349
;102/38 ;244/3.16,14 ;343/17.7 ;356/152 ;273/98,101,105.3 ;240/1A
;40/13R ;73/1R,1F ;219/553 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Lawrence; James W.
Assistant Examiner: Willis; Davis L.
Attorney, Agent or Firm: Sciascia; R. S. Miller; Roy Baker;
Gerald F.
Claims
What is claimed is:
1. Target simulating apparatus for investigating operational
efficiency of a light energy sensitive tracking system having a
finite viewing envelope;
said target simulating apparatus including;
a plurality of illuminable elements arranged to emit radiant energy
waves toward said tracking system within the viewing envelope of
said system;
means for individually illuminating selected ones of said elements;
and
means for illuminating said elements in timed sequence.
2. The apparatus of claim 1 wherein said elements are arranged in a
plane orthogonal to the longitudinal axis of said viewing envelope
and each element, when illuminated, emits radiation in a particular
prearranged angular direction in relation to said axis.
3. The apparatus of claim 2 wherein said elements are arranged in a
plurality of linear arrays forming roughly a square having sides
approximately equidistant from said axis.
4. The apparatus of claim 3 wherein said angular relationship
varies:
a. along a first side of said square from 0.degree. to 10.degree.
in a first direction(x);
b. along a second side from 2.degree. to 10.degree. in a second
direction (y) orthogonal to said first direction;
c. along a third side from 2.degree. to 10.degree. in said
direction (x); and
d. along the fourth side from 2.degree. to 10.degree. in said
direction (y).
5. The apparatus of claim 4 wherein said elements are electrically
excitable infrared radiating devices and said means for
illuminating said elements includes a source of regular electrical
pulses of a predetermined frequency and electrical logic circuitry
for controlling application of current to said devices.
6. The apparatus of claim 3 wherein said elements are electrically
excitable infrared radiating devices and said means for
illuminating said elements includes a source of regular electrical
pulses of a predetermined frequency and electrical logic circuitry
for controlling application of current to said devices.
7. The apparatus of claim 2 wherein said elements are electrically
excitable infrared radiating devices and said means for
illuminating said elements includes a source of regular electrical
pulses of a predetermined frequency and electrical logic-circuitry
for controlling application of current to said devices.
8. The apparatus of claim 2 wherein said elements are arranged in a
plurality of linear arrays and wherein said angular direction for
diodes in each array range from 2.degree. to 10.degree. and one
additional element arranged to emit rays essentially parallel to
said axis.
Description
BACKGROUND OF THE INVENTION
This invention relates to testing systems and more particularly to
target simulating systems for testing tracking apparatus. More
particularly the invention relates to the simulation of moving
target reflected radiation to test laser guided missile seekers
before flight.
As missile guidance and control systems become more sophisticated,
the price of the missile rises and it is increasingly important to
test the guidance and control system thoroughly before certifying
the missile to use. It is especially advantageous to be able to
final test on the aircraft. The target simulator and test equipment
according to the present invention is designed to ensure that the
guidance and control system of a laser guided missile, for example,
is in proper working order. The system may be used with the missile
before delivery to a launching vehicle or may be adapted for use
with the missile in place on the aircraft.
SUMMARY OF THE INVENTION
The simulation of a moving light emitting target is accomplished by
sequencing a plurality of small light emitting diodes at a rate not
exceeding the tracking rate of the laser seeker being tested.
Digital circuitry is used to determine the sequence and the timing
of the sequence. Digital circuitry is also provided which gives the
capability to manually sequence the diodes as desired. The diodes
emit a collimated beam of energy at different angles to the
longitudinal axis of the missile.
By visually observing either the seeker head activity or
instrumentation attached to the missile, the capability of the
seeker tracking unit can be determined before flight. This may be
accomplished with the missile attached to the aircraft by observing
the instrumentation in the aircraft.
The test equipment may be arranged in a housing which can be
quickly and securely fixed to a missile nose section in a
predetermined position with respect to the seeker unit.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING
FIG. 1 is a diagrammatic view constituting a schematic illustration
of a system according to the invention;
FIG. 2 is an exploded view of one embodiment of a target simulator
useable with the system of FIG. 1;
FIG. 3 is a plan view of the diode carrier of FIG. 2;
FIG. 4 is a side elevational view of the carrier of FIG. 3 partly
in section;
FIG. 5 is an enlarged cross sectional view taken along line V--V of
FIG. 3; and
FIG. 6 is a simplified diagram of a switching logic circuit useable
with the system.
DESCRIPTION AND OPERATION
As shown in FIG. 1, the test arrangement 10 comprises a target
simulator 12 aligned with the nose section 14 of a guided missile,
for example, on a test stand 15. The simulator 12 comprises a
linear array 13 of small light-emitting diodes 17 actuated by
driver circuitry 16 under the control of logic circuit means
18.
When any of the diodes 17 in array 13 are "illuminated," they emit
infrared rays (represented by broken line) which are beamed through
the window 20 of nose section 14 and these rays impinge on a
toroidal parabolic primary mirror 24 which focuses the rays on a
secondary mirror 26 which in turn reflects the rays to detector
means 28. Detector means 28 generates pulses in accordance with
directional parameters of the received radiation. The pulses
generated are then applied to the missile logic section 29 in the
nose section of the missile.
In the arrangement shown in FIG. 1, the output of the logic
circuitry 29 is indicated on a test panel 30. When the unit is used
in the field, however, the indication may be exhibited on a cockpit
display panel, for example, in an aircraft. The target simulator 12
is connected to switching logic circuitry 18 through which the
diodes 17 may be sequentially illuminated to simulate rays
emanating from a moving target. A power supply 32 and an oscillator
34 supply the necessary current to the simulator.
The detector 28 is a four quadrant IR detector which is affected by
the angle in which the rays are received. The missile seeker system
being tested is designed to correct for the amount of deviation of
the beam angle from the missile seeker line axis.
The target simulator 12 comprises a sequencing infrared source that
uses five binary coded inputs to select the desired target. One
input is utilized to select either azimuth or elevation and the
other four inputs are used to select infrared sources from
-10.degree. to +10.degree. in 2.degree. increments. The binary code
input allows one infrared source to emit at a time and allows the
selection of any one source at any desired time, that is, the
target simulator does not have to be sequenced, it can step from -
10.degree. to 0.degree. in one step.
The target simulator situation differs from actual conditions in
that the target simulator 12 does not flood the entire mirror area
but uses only a one quarter inch column of parallel light rays. The
results and the reaction of the missile tracking system 29,
however, is the same. The light emitting diodes 17 are actuated by
diode drivers 16 in response to signals from switching logic panel
18.
The diodes 17 may be arranged in orthogonal linear array or any
other desired pattern within the viewing envelope of the
missile.
In addition to the laboratory type arrangement of FIG. 1, the diode
array may be fastened directly to the missile nose 14, shown in
FIG. 2. The nose of the missile has an annular groove 35 which may
be used to fasten the diode carrier 36 using a split collar 38 and
an adaptor 40. The collar 38 has an internal contour 39
complementary to the contour of the missile nose at groove 35.
The collar is installed around nose 14 of the missile at groove 35
and fastened by means of a clamp 41. The collar carries three
similar clamp members 42 designed to interact with hooks 43 on
adapter 40. When thus connected, the collar and adaptor form a
hollow integral light shield around missile window 20.
The diode carrier 36 is fastened in place in the forward end of
adaptor 40 and protected by a cover 44. Carrier 36 is shown with an
"O" ring 45 installed in a peripheral groove to aid in preventing
dust and moisture from penetrating under the cover 44 when the unit
is assembled. In practice, the diode carrier 36 remains assembled
to the adaptor 40 with the cover 44 in place unless disassembly is
necessary, for example, for repair.
A preferred arrangement of the diodes in carrier 36 is shown in
FIG. 3. Although a simple orthogonal intersecting pattern was used
satisfactorily in early models, the diode array shown in FIG. 3 has
been found to be more versatile, covering a greater area of the
missile optics with a minimum size of the diodes array.
It will be noted that only the diode mounted in hole K1 will be on
boresight parallel to the missile axis. The remainder of the diodes
are mounted in holes in four rows forming roughly the sides of a
square superimposed on the torroidal field of view of the missile
optics at the close range of the test unit. The row of holes M1
through M5 is typical and the angular placement of the holes is
more clearly shown in FIG. 5. FIG. 3 also shows four holes used for
mounting the carrier to adaptor 40 and one hole 46 which mates with
a locator pin (not shown) to ensure proper alignment of carrier and
adaptor during assembly.
FIG. 4 shows the shape of carrier 36 and the "O" ring groove 47
around the periphery.
FIG. 5 shows the boresight diode hole K1 and the holes M1 through
M5 ranging from 2.degree. to 10.degree. angle to boresight. The
rows N, H and J shown in FIG. 3 are similarly arranged with respect
to boresight and two imaginary lines X and Y orthogonally
intersecting the line of boresight. In the table below the legend
.angle. to 'X' indicates deviation from boresight along line X and
.angle. to 'Y' means that deviation from boresight along line
Y.
______________________________________ HOLE DATA
______________________________________ HOLE .angle. TO 'X' .angle.
TO 'Y' SYMBOL .+-. 0.degree.2' .+-.0.degree.2'
______________________________________ H1 2.degree. 0.degree. H2
4.degree. 0.degree. H3 6.degree. 0.degree. H4 8.degree. 0.degree.
H5 10.degree. 0.degree. J1 0.degree. 2.degree. J2 0.degree.
4.degree. J3 0.degree. 6.degree. J4 0.degree. 8.degree. J5
0.degree. 10.degree. K1 0.degree. 0.degree. M1 2.degree. 0.degree.
M2 4.degree. 0.degree. M3 6.degree. 0.degree. M4 8.degree.
0.degree. M5 10.degree. 0.degree. N1 0.degree. 2.degree. N2
0.degree. 4.degree. N3 0.degree. 6.degree. N4 0.degree. 8.degree.
N5 0.degree. 10.degree. ______________________________________
The diodes 17 fit into the holes and are held against a shoulder 48
by a compression spring 50 which is held in place by a lock ring 52
fitted into a groove 53 in the side wall of the hole. The
electrical leads 54 of the diodes are led through the center of
springs 50 to connection boards (not shown) which may be fastened
to the surface of carrier 36. The electrical system of target
simulator 12 is schematically shown in FIG. 6.
The power supply 32 furnishes power to the system through a Master
switch 54 and a series of control switches shown on the left hand
side of the FIG. 6 diagram.
Switches 55, 56 and 57 may be used to manually select either the
+2.degree. diode M1, the 0.degree. diode K1 or the -2.degree. diode
H1 respectively, for example, to align the test set with the
missile system. Switch 58 selects the direction of sequencing of
the diodes. The reset & function actuate switch 59 is a
three-position switch, normally open, and may be positioned in the
function actuate or in the reset position as desired. To actuate
the test arrangement, switch 59 is placed in its lower or function
actuate position. When switch 59 is moved to the reset or upper
position, the system returns to a condition in which the
-10.degree. diode H5 is ON (See FIG. 3).
The automatic-manual switch 60 is normally in the automatic mode
but may be switched to the lower or manual position as desired.
The diode ON/OFF switch 61 is provided so that the light emitting
diodes may be turned off leaving the remainder of the system on
standby.
Selection is made through the operation of an Up-Down Counter 62
and a Decoder 64 with associated flip flops 66, 68 ythrough logic
NAND gates 70-76 and AND gates 80, 82 and 84.
When the Diode ON/OFF switch, 61, is placed in the lower position
in FIG. 2, voltage (Logic ONE) is supplied to inhibit decoder 64.
If the automatic-manual switch 60 is in the upper position as
shown, a logic ONE will be supplied to the NAND Gates 74 and 76.
With the Left-to-Right and Right-to-Left switch 58 in the upper
position as shown, a logic ONE will be supplied to NAND gate 71 and
AND gate 82. At the same time switch 58 places a Logic Zero on NAND
gate 70 and AND gate 84. Also with switches 55, 56 and 57 in
position shown, a logic ONE will be supplied to input terminal C of
the up-down counter 62 and terminals, A, B and C will be at
ZERO.
Desiring now to actuate the mechanism, if the Reset-actuate switch
59 be placed in the lower position, then a logic ONE will be
supplied to flip flop (one shot) 68. When the decoder 64 is at
rest, the outputs to the diode drivers 16 and to NAND gate 72 is at
a logic ZERO. A logic zero on NAND gate 72 causes a logic ONE
output which enables the AND gate 82 which puts a logic ONE on NAND
gate 75 allowing the clock pulse from the oscillator to carry
through. Since 74 and 76 were already enabled there is an output
signal from 76 of alternating ONE-ZERO going to AND Gate 80, which
has a logic ONE applied to the other terminal, as related above.
Thus we get a logic ONE-ZERO alternating from AND gate 80 going to
NAND gate 70. The other terminal of gate 70 has already been
enabled as stated above, an alternating ONE-ZERO signal goes to the
up-down counter 62. The counter 62 then starts counting in one
direction or the other and signals are presented to the decoder 64.
These signals cause the decoder 64 to start outputting signals from
eleven output terminals in sequence to various terminals of diode
drivers 16.
These signals from decoder 64 in turn activate diode drivers 16
through enabling circuitry to light up the light emitting diodes in
sequence. When the last light emitting diode is illuminated in the
right to left direction, the system comes to rest with the output
terminals of decoder 64 in a ZERO condition and, in order to start
the system again, the Left-Right switch must be changed to its
opposite position and the Function Actuate switch again
depressed.
* * * * *